PILOT’S OPERATING HANDBOOK AND FAA APPROVED AIRPLANE FLIGHT MANUAL for the CIRRUS SR22T

7-27 Revision 1 7-28 Revision 1 7-29 Revision 1 7-30 Revision 1 7-31 Revision 1 7-32 Revision 1 7-33 Revision 1 7-34 Revision 1 7-35 Revision 1 7-36 Revision 1 7-37 Revision 1 7-38 Revision 1 7-39 Revision 1 7-40 Revision 1 7-41 Revision 1 7-42 Revision 1 7-43 Revision 1 7-44 Revision 1 7-45 Revision 1 7-46 Revision 1 7-47 Revision 1 7-48 Revision 1 7-49 Revision 1 7-50 Revision 1 7-51 Revision 1 7-52 Revision 1 7-53 Revision 1 7-54 Revision 1 7-55 Revision 1 7-56 Revision 1 7-57 Revision 1 7-58 Revision 1 7-59 Revision 1 7-60 Revision 1 7-61 Revision 1 7-62 Revision 1 7-63 Revision 1 7-64 Revision 1 7-65 Revision 1 7-66 Revision 1 7-67 Revision 1 7-68 Revision 1 7-69 Revision 1 7-70 Revision 1 7-71 Revision 1 7-72 Revision 1 7-73 Revision 1 7-74 Revision 1 7-75 Revision 1 7-76 Revision 1 Revision 1 P/N 13772-005 C Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status 7-77 Revision 1 7-78 Revision 1 7-79 Revision 1 7-80 Revision 1 7-81 Revision 1 7-82 Revision 1 7-83 Revision 1 7-84 Revision 1 7-85 Revision 1 7-86 Revision 1 7-87 Revision 1 7-88 Revision 1 7-89 Revision 1 7-90 Revision 1 7-91 Revision 1 7-92 Revision 1 7-93 Revision 1 7-94 Revision 1 7-95 Revision 1 7-96 Revision 1 7-97 Revision 1 7-98 Revision 1 7-99 Revision 1 7-100 Revision 1 7-101 Revision 1 7-102 Revision 1 7-103 Revision 1 7-104 Revision 1 7-105 Revision 1 7-106 Revision 1 7-107 Revision 1 7-108 Revision 1 8-1 Revision 1 8-2 Original Issue 8-3 Revision 1 8-4 Revision 1 8-5 Original Issue 8-6 Original Issue 8-7 Original Issue 8-8 Original Issue 8-9 Original Issue 8-10 Original Issue 8-11 Revision 1 8-12 Original Issue 8-13 Original Issue 8-14 Original Issue 8-15 Original Issue 8-16 Revision 1 8-17 Revision 1 8-18 Revision 1 8-19 Revision 1 8-20 Original Issue 8-21 Original Issue 8-22 Original Issue 8-23 Revision 1 8-24 Revision 1 8-25 Original Issue 8-26 Original Issue 8-27 Revision 1 8-28 Revision 1 8-29 Revision 1 8-30 Revision 1 8-31 Revision 1 8-32 Revision 1 8-33 Revision 1 8-34 Revision 1 8-35 Revision 1 8-36 Revision 1 8-37 Revision 1 8-38 Revision 1 9-1 Revision 1 9-2 Original Issue 10-1 Original Issue 10-2 Original Issue 10-3 Original Issue 10-4 Original Issue 10-5 Original Issue 10-6 Original Issue 10-7 Original Issue 10-8 Original Issue 10-9 Revision 1 10-10 Original Issue 10-11 Original Issue 10-12 Revision 1 10-13 Revision 1 10-14 Revision 1 Revision 1 D P/N 13772-005 Cirrus Design Pilot’s Operating Handbook SR22T List of Effective Pages List of Effective Pages (Cont.) Page Status Page Status Page Status Original Issue Intentionally Left Blank Cirrus Design Front Matter SR22T Foreword P/N 13772-005 Front Matter-1 P/N 13772-005 Front Matter-1 Foreword This Pilot’s Operating Handbook (POH) has been prepared by Cirrus Design Corporation to familiarize operators with the aircraft. Read this POH carefully. It provides operational procedures that will assure the operator obtains the performance published in the manual, data designed to allow the most efficient use of the airplane, and basic information for maintaining the airplane in a “like new” condition. • Note • All limitations, procedures, maintenance & servicing requirements, and performance data contained in this POH are mandatory for compliance with FAA operating rules and for continued airworthiness of the airplane. This POH includes the material required to be furnished to the pilot by the Federal Aviation Regulations (FARs) and additional information provided by Cirrus Design Corporation and constitutes the FAA Approved Airplane Flight Manual for the aircraft. Revision 1 Front Matter-2 P/N 13772-005 Front Matter Cirrus Design Foreword SR22T The Pilot’s Operating Handbook This Pilot’s Operating Handbook has been prepared using GAMA Specification #1 for Pilot’s Operating Handbook, Revision 2, dated 18 October 1996 as the content model and format guide. However, some deviations from this specification were made for clarity. The POH is presented in loose-leaf form for ease in inserting revisions and is sized for convenient storage. Tabbed dividers throughout the POH allow quick reference to each section. Logical and convenient Tables of Contents are located at the beginning of each section to aid in locating specific data within that section. The POH is divided into ten sections as follows: Section 1................................................................................... General Section 2...............................................................................Limitations Section 3.......................................................... Emergency Procedures Section 3A .......................................................... Abnormal Procedures Section 4................................................................. Normal Procedures Section 5...................................................................Performance Data Section 6...........................................Weight & Balance/Equipment List Section 7............................................................... Systems Description Section 8........................................ Handling, Servicing & Maintenance Section 9........................................................................... Supplements Section 10.................................................................Safety Information The data presented in this POH is the result of extensive flight tests and is approved by the Federal Aviation Administration. However, as new procedures or performance data are developed, the POH will be revised. • Note • It is the responsibility of the owner to ensure that the Pilot’s Operating Handbook is current at all times. Therefore, it is very important that all revisions be properly incorporated into this POH as soon as they are available. Revision 1 Cirrus Design Front Matter SR22T Foreword P/N 13772-005 Front Matter-3 P/N 13772-005 Front Matter-3 Revising the Pilot’s Operating Handbook Two types of revisions may be issued for this POH: Temporary and Numbered. Temporary revisions are printed on yellow paper, normally cover only one topic or procedure, and are issued to provide safety related information or other time sensitive information where the rigor of providing a numbered revision is not possible in the time allowed. All the information needed to properly file a temporary revision is included on the revision itself. Typically, a temporary revision is superseded and replaced by the next numbered revision. Numbered revisions are printed on white paper, normally cover several subjects, and are issued as general updates to the POH. Each numbered revision includes an “Instruction Sheet,” a “List of Effective Pages”, and a “Revision Highlights” page. The “Instruction Sheet” is intended to assist the manual holder in removing superseded pages and inserting new or superseding pages. The “List of Effective Pages” shows the issue or revision status of all pages in the POH. The “Revision Highlights” page gives a brief description of changes made to each page in the current revision. Identifying Revised Material Each page in the POH has revision identification at the lower inside corner opposite the page number. Original issue pages will be identified by the words “Original Issue” at this location. In the event that the majority of pages in the POH are revised, Cirrus may determine that it is more effective to reissue the POH. Reissued pages will be identified by the word “Reissue” followed by a letter indicating the reissue level; for example, “Reissue A” Revised pages will be identified by the word “Revision” followed by the revision number at this location; for example, “Revision 2” (Original Issue, Revision 2) or “Revision B1” (Reissue B, Revision 1). Revised material on a page can be identified by a change bar located at the outside page margin. Revision bars are not used at reissues of the POH. Revision 1 Front Matter-4 P/N 13772-005 Front Matter Cirrus Design Foreword SR22T Revisions to the Pilot’s Operating Handbook POH revisions, temporary revisions, and supplements can be downloaded from Cirrus Design at www.cirrusaircraft.com, or from the Authorized Service Center website. Paper copies of POH revisions and supplements can be purchased from Cirrus Connection at www.cirrusconnection.com. • Note • If at any time it is found that the POH is not current, temporary revisions are missing, or applicable supplements are not included, contact Cirrus Design. Supplements The Supplements section (Section 9) of this POH contains FAA Approved Supplements necessary to safely and efficiently operate the airplane when equipped with optional equipment not provided with the standard airplane or not included in the POH. Supplements are essentially “mini-handbooks” and may contain data corresponding to most sections of the POH. Data in a supplement either adds to, supersedes, or replaces similar data in the basic POH. Section 9 includes a “Log of Supplements” page preceding all Cirrus Design Supplements produced for this airplane. The “Log of Supplements” page can be utilized as a “Table of Contents” for Section 9. If the airplane is modified at a non Cirrus Design facility through an STC or other approval method, it is the owner’s responsibility to ensure that the proper supplement, if applicable, is installed in the POH and that the supplement is properly recorded on the “Log of Supplements” page. FAA Approved POH Supplements must be in the airplane for flight operations when the subject optional equipment is installed or the special operations are to be performed. Retention of Data In the event a new title page is issued, the weight and balance data changes, the equipment list changes, or the “Log of Supplements” is replaced, the owner must ensure that all information applicable to the airplane is transferred to the new pages and the aircraft records are current. It is not a requirement that owners retain information, such as supplements, that is not applicable to their airplane. Revision 1 Cirrus Design Front Matter SR22T Foreword P/N 13772-005 Front Matter-5 P/N 13772-005 Front Matter-5 In the event a new POH is purchased, the owner must ensure that all information applicable to the airplane is transferred to the new POH and the aircraft records are current. Warnings, Cautions, and Notes Warnings, Cautions, and Notes are used throughout this POH to focus attention on special conditions or procedures as follows: • WARNING • Warnings are used to call attention to operating procedures which, if not strictly observed, may result in personal injury or loss of life. • Caution • Cautions are used to call attention to operating procedures which, if not strictly observed, may result in damage to equipment. • Note • Notes are used to highlight specific operating conditions or steps of a procedure. Revision 1 Front Matter-6 P/N 13772-005 Front Matter Cirrus Design Foreword SR22T Original Issue Intentionally Left Blank P/N 13772-005 1-1 Cirrus Design Section 1 SR22T General Introduction ........................................................................................ 3 The Airplane....................................................................................... 7 Engine............................................................................................. 7 Propeller ......................................................................................... 7 Fuel................................................................................................. 8 Oil .................................................................................................. 8 Maximum Certificated Weights ....................................................... 8 Cabin and Entry Dimensions .......................................................... 8 Baggage Spaces and Entry Dimensions ........................................ 8 Specific Loadings............................................................................ 8 Symbols, Abbreviations and Terminology.......................................... 9 General Airspeed Terminology and Symbols ................................. 9 Meteorological Terminology.......................................................... 10 Engine Power Terminology........................................................... 11 Performance and Flight Planning Terminology............................. 12 Weight and Balance Terminology................................................. 12 Original Issue Section 1: General Table of Contents 1-2 P/N 13772-005 Section 1 Cirrus Design General SR22T Original Issue Intentionally Left Blank Cirrus Design Section 1 SR22T General P/N 13772-005 1-3 P/N 13772-005 1-3 Introduction This section contains information of general interest to pilots and owners. You will find the information useful in acquainting yourself with the airplane, as well as in loading, fueling, sheltering, and handling the airplane during ground operations. Additionally, this section contains definitions or explanations of symbols, abbreviations, and terminology used throughout this handbook. • Note • For specific information regarding the organization of this Handbook, revisions, supplements, and procedures to be used to obtain publications, see the “Foreword” section. All liquid volumes referenced in this publication are expressed in United States Customary Units, e.g., U.S. Gallons. Revision 1 1-4 P/N 13772-005 Section 1 Cirrus Design General SR22T Figure 1-1 Airplane Three View 78 inches 3-BLADE 198 cm 38.3 ft 11.67 m 9.1 ft 2.8 m 9 inches (minimum) 23 cm (minimum) 26.0 ft 7.92 m 8.9 ft 2.71 m NOTE: • Wing span includes position and strobe lights. • Prop ground clearance - 9" inches (23 cm). • Wing Area = 144.9 sq. ft. SR22_FM01_3550 Original Issue Cirrus Design Section 1 SR22T General P/N 13772-005 1-5 P/N 13772-005 1-5 Location Length Width Height Volume Cabin 122” 49.3” 49.7 137 cu ft Baggage Compartment 36” 39.8” 38.5” 32 cu ft Figure 1-2 Airplane Interior Dimensions 39.8" 49.3" 240 220 200 180 160 140 120 16.0" 49.7" 27.0" 38.5" FS 10.5" 33.4" 39.0" 20.0" 33.3" 32.0" SR22_FM01_1019A 100 222 CABIN DOOR OPENING BAGGAGE DOOR OPENING 20.0" 21.0" 5.0" Station Fuselage Original Issue 1-6 P/N 13772-005 Section 1 Cirrus Design General SR22T Figure 1-3 Turning Radius 9.1 ft. (2.77 m) 0.5 ft. (0.15 m) 24.3 ft. (7.41 m) 7.0 ft. (2.16 m) RADIUS FOR NOSE GEAR RADIUS FOR OUTSIDE GEAR RADIUS FOR INSIDE GEAR RADIUS FOR WING TIP TURNING RADII ARE CALCULATED USING ONE BRAKE AND PARTIAL POWER. ACTUAL TURNING RADIUS MAY VARY AS MUCH AS THREE FEET. GROUND TURNING CLEARANCE SR22_FM01_2412 Original Issue Cirrus Design Section 1 SR22T General P/N 13772-005 1-7 P/N 13772-005 1-7 The Airplane Engine Number of Engines.............................................................................. 1 Engine Manufacturer ............................................Teledyne Continental Engine Model .....................................................................TSIO-550-K Engine Type ........ Turbocharged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine with 550 cubic inch displacement. Horsepower Rating.............................................. 315 bhp @ 2500 rpm Propeller Hartzell Compact Series Lightweight Hub with Composite Blades Propeller Type ........................................ Constant Speed, Three Blade Model Number..............................................PHC-J3Y1F-1N/N7605(B) Diameter........................................................................................78.0" Model Number........................................... PHC-J3Y1F-1N/N7605C(B) Diameter........................................................................................78.0" Original Issue 1-8 P/N 13772-005 Section 1 Cirrus Design General SR22T Fuel Total Capacity ............................................ 94.5 U.S. Gallons (358.0 L) Total Usable.............................................. .92.0 U.S. Gallons (348.0 L) Approved Fuel Grades: 100 LL Grade Aviation Fuel (Blue) 100 (Formerly 100/130) Grade Aviation Fuel (Green) Oil Oil Capacity (Sump) .............................................8 U.S. Quarts (7.6 L) Oil Grades: All Temperatures ...................................... 15W-50, 20W-50 or 20W-60 Above 40°F (4°C) .......................................SAE 50, 20W50, or 20W60 Below 40°F (4°C).......................... SAE 30, 10W30, 15W50, or 20W50 Maximum Certificated Weights Maximum Gross for Takeoff...................................... 3600 lb (1633 Kg) Maximum Zero Fuel Weight ..................................... 3400 lb (1542 Kg) Maximum Baggage Compartment Loading .................... 130 lb (59 Kg) Cabin and Entry Dimensions Refer to the preceding figures for dimensions of the cabin interior and entry door openings. Baggage Spaces and Entry Dimensions Refer to the preceding figures for dimensions of the baggage area and baggage door opening. Specific Loadings Wing Loading..................................................... 24.8 lb per square foot Power Loading................................................................. 11.4 lb per hp Revision 1 Cirrus Design Section 1 SR22T General P/N 13772-005 1-9 P/N 13772-005 1-9 Symbols, Abbreviations and Terminology General Airspeed Terminology and Symbols KCAS Knots Calibrated Airspeed is the indicated airspeed corrected for position and instrument error. Calibrated airspeed is equal to true airspeed in standard atmosphere at sea level. KIAS Knots Indicated Airspeed is the speed shown on the airspeed indicator. The IAS values published in this handbook assume no instrument error. KTAS Knots True Airspeed is the airspeed expressed in knots relative to undisturbed air which is KCAS corrected for altitude and temperature. V G Best Glide Speed is the speed at which the greatest flight distance is attained per unit of altitude lost with power off. V O Operating Maneuvering Speed is the maximum speed at which application of full control movement will not overstress the airplane. V FE Maximum Flap Extended Speed is the highest speed permissible with wing flaps in a prescribed extended position. V NO Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air, and then only with caution. V NE Never Exceed Speed is the speed that may not be exceeded at any time. V PD Maximum Demonstrated Parachute Deployment Speed is the maximum speed at which parachute deployment has been demonstrated. V REF Landing reference speed or threshold crossing speed. V S Stalling Speed is minimum steady flight speed at which the aircraft is controllable. Original Issue 1-10 P/N 13772-005 Section 1 Cirrus Design General SR22T Meteorological Terminology V S 50% Stalling Speed is minimum steady flight speed at which the aircraft is controllable with 50% flaps. V SO Stalling Speed is the minimum steady flight speed at which the aircraft is controllable in the landing configuration (100% flaps) at the most unfavorable weight and balance. V X Best Angle of Climb Speed is the speed at which the airplane will obtain the highest altitude in a given horizontal distance. The best angle-of-climb speed normally increases slightly with altitude. V Y Best Rate of Climb Speed is the speed at which the airplane will obtain the maximum increase in altitude per unit of time. The best rate-of-climb speed decreases slightly with altitude. IMC Instrument Meteorological Conditions are meteorological conditions expressed in terms of visibility, distance from cloud, and ceiling less than the minima for visual flight defined in FAR 91.155. ISA International Standard Atmosphere (standard day) is an atmosphere where (1) the air is a dry perfect gas, (2) the temperature at sea level is 15°C, (3) the pressure at sea level is 29.92 in.Hg (1013.2 millibars), and (4) the temperature gradient from sea level to the altitude at which the temperature is - 56.5°C is -0.00198°C per foot and zero above that altitude. MSL Mean Sea Level is the average height of the surface of the sea for all stages of tide. In this Handbook, altitude given as MSL is the altitude above the mean sea level. It is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to the altimeter setting obtained from ground meteorological sources. Original Issue Cirrus Design Section 1 SR22T General P/N 13772-005 1-11 P/N 13772-005 1-11 Engine Power Terminology OAT Outside Air Temperature is the free air static temperature obtained from inflight temperature indications or from ground meteorological sources. It is expressed in either degrees Celsius or degrees Fahrenheit. Pressure Altitude Pressure Altitude (PA) is the altitude read from the altimeter when the altimeter’s barometric adjustment has been set to 29.92 in.Hg (1013 mb) corrected for position and instrument error. In this Handbook, altimeter instrument errors are assumed to be zero. Standard Temperature Standard Temperature is the temperature that would be found at a given pressure altitude in the standard atmosphere. It is 15°C (59°F) at sea level pressure altitude and decreases approximately 2°C (3.6°F) for each 1000 feet of altitude increase. See ISA definition. BHP Brake Horsepower is the power developed by the engine. MCP Maximum Continuous Power is the maximum power that can be used continuously. MAP Manifold Pressure is the pressure measured in the engine’s induction system expressed as inches of mercury (in.Hg). RPM Revolutions Per Minute is engine rotational speed. Static RPM Static RPM is RPM attained during a full-throttle engine runup when the airplane is on the ground and stationary. TIT Turbine Inlet Temperature is the temperature measured in front of the first stage turbine nozzle valves. Original Issue 1-12 P/N 13772-005 Section 1 Cirrus Design General SR22T Performance and Flight Planning Terminology Weight and Balance Terminology g One “g” is a quantity of acceleration equal to that of earth’s gravity. Demonstrated Crosswind Velocity Demonstrated Crosswind Velocity is the velocity of the crosswind component for which adequate control of the airplane during taxi, takeoff, and landing was actually demonstrated during certification testing. Demonstrated crosswind is not considered to be limiting. Service Ceiling Service Ceiling is the maximum altitude at which the aircraft at maximum weight has the capability of climbing at a rate of 100 feet per minute. GPH Gallons Per Hour is the amount of fuel (in gallons) consumed by the aircraft per hour. NMPG Nautical Miles Per Gallon is the distance (in nautical miles) which can be expected per gallon of fuel consumed at a specific engine power setting and/or flight configuration. Unusable Fuel Unusable Fuel is the quantity of fuel that cannot be safely used in flight. Usable Fuel Usable Fuel is the fuel available for flight planning. Reference Datum Reference Datum is an imaginary vertical plane from which all horizontal distances are measured for balance purposes. Station Station is a location along the airplane fuselage measured in inches from the reference datum and expressed as a number. For example: A point 123 inches aft of the reference datum is Fuselage Station 123.0 (FS 123). CG Center of Gravity is the point at which an airplane would balance if suspended. Its distance from the reference datum is found by dividing the total moment by the total weight of the airplane. Original Issue Cirrus Design Section 1 SR22T General P/N 13772-005 1-13 P/N 13772-005 1-13 Arm Arm is the horizontal distance from the reference datum to the center of gravity (CG) of an item. The airplane’s arm is obtained by adding the airplane’s individual moments and dividing the sum by the total weight. Moment Moment is the product of the weight of an item multiplied by its arm. Standard Empty Weight Standard Empty Weight is the weight of a standard airplane including unusable fuel, full operating fluids, and full oil Basic Empty Weight Basic Empty Weight is the actual weight of the airplane including all operating equipment that has a fixed location in the airplane. The basic empty weight includes the weight of unusable fuel and full oil. Maximum Ramp Weight Maximum Ramp Weight is the maximum weight approved for ground maneuver and includes the weight of the fuel used for startup, taxi, and run-up. Maximum Gross Weight Maximum Gross Weight is the maximum permissible weight of the airplane and its contents as listed in the aircraft specifications. Maximum Zero Fuel Weight Maximum Zero Fuel Weight is the maximum permissible weight of the airplane and its contents minus the total weight of the fuel onboard. Useful Load Useful Load is the basic empty weight subtracted from the maximum ramp weight. It is the maximum allowable combined weight of pilot, passengers, fuel and baggage. MAC Mean Aerodynamic Chord is the chord drawn through the centroid of the wing plan area. LEMAC Leading Edge of Mean Aerodynamic Chord is the forward edge of MAC given in inches aft of the reference datum (fuselage station). Original Issue 1-14 P/N 13772-005 Section 1 Cirrus Design General SR22T Tare Tare is the weight of all items used to hold or position the airplane on the scales for weighing. Tare includes blocks, shims, and chocks. Tare weight must be subtracted from the associated scale reading. Original Issue P/N 13772-005 2-1 Cirrus Design Section 2 SR22T Limitations Introduction ........................................................................................ 3 Certification Status ............................................................................. 3 Airspeed Limitations........................................................................... 4 Airspeed Indicator Markings .............................................................. 5 Powerplant Limitations ....................................................................... 6 Engine............................................................................................. 6 Operating Limits.............................................................................. 6 Approved Oils: ................................................................................ 6 Fuel Grade..................................................................................... :7 Weight Limits ..................................................................................... 7 Engine Instrument Markings & Annunciations ................................... 8 PowerPlant ..................................................................................... 8 Fuel................................................................................................. 9 Electrical ......................................................................................... 9 Center of Gravity Limits ................................................................... 10 Maneuver Limits............................................................................... 11 Flight Load Factor Limits.................................................................. 11 Minimum Flight Crew ....................................................................... 11 Kinds of Operation ........................................................................... 12 Kinds of Operation Equipment List ............................................... 12 Icing .............................................................................................. 16 Runway Surface ........................................................................... 16 Taxi Power.................................................................................... 17 Fuel Limits........................................................................................ 17 Altitude Limits................................................................................... 17 Environmental Conditions ................................................................ 17 Maximum Occupancy ...................................................................... 18 Systems and Equipment Limits........................................................ 19 Cirrus Perspective Integrated Avionics System ............................ 19 L-3 Skywatch Traffic Advisory System (Optional)......................... 22 L-3 Stormscope Weather Information System (Optional) ............. 22 Max Viz Enhanced Vision System (Optional) ............................... 23 MD302 Standby Attitude Module (Optional) ................................. 23 Air Conditioning System (Optional)............................................... 23 Inflatable Restraint System........................................................... 23 Flap Limitations............................................................................. 23 Revision 1 Section 2: Limitations Table of Contents 2-2 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Paint.............................................................................................. 24 Cirrus Airframe Parachute System (CAPS) ..................................24 Other Limitations .............................................................................. 24 Smoking ........................................................................................ 24 Placards ........................................................................................... 25 Revision 1 Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-3 P/N 13772-005 2-3 Introduction The limitations included in this Section of the Pilot’s Operating Handbook (POH) are approved by the Federal Aviation Administration. This section provides operating limitations, instrument markings and basic placards required by regulation and necessary for the safe operation of the aircraft and its standard systems and equipment. Refer to Section 9: Log of Supplements of this handbook for amended operating limitations for airplanes equipped with optional equipment. Compliance with the operating limitations in this section and in Section 9 is required by Federal Aviation Regulations. • Note • Limitations associated with optional equipment are not described in this section. For optional equipment limitations, refer to Section 9: Log of Supplements. Certification Status The aircraft is certificated under the requirements of Federal Aviation Regulations (FAR) Part 23 as documented by FAA Type Certificate TC A00009CH. Original Issue 2-4 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Airspeed Limitations The indicated airspeeds in the following table are based on Section 5, Airspeed Calibration: Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. Speed KIAS KCAS Remarks VNE up to 17,500 feet MSL 205 208 Never Exceed Speed is the speed that may not be exceeded at any time. VNE at 25,000 feet MSL 175 178 V NE is reduced linearly from 17,500 feet to 25,000 feet. VNO up to 17,500 feet MSL 176 179 Maximum Structural Cruising Speed is the speed that should not be exceeded except in smooth air and then only with caution. VNO at 25,000 feet MSL 150 153 V NO is reduced linearly from 17,500 feet to 25,000 feet. VO 3600 Lb 140 142 Operating Maneuvering Speed is the maxi- mum speed at which full control travel may be used. Below this speed the airplane stalls before limit loads are reached. Above this speed, full control movements can damage the airplane. VFE 50% Flaps 100% Flaps 150 110 152 111 Maximum Flap Extended Speed is the high- est speed permissible with wing flaps extended. VPD 140 142 Maximum Demonstrated Parachute Deployment Speed is the maximum speed at which parachute deployment has been demonstrated. Original Issue Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-5 P/N 13772-005 2-5 Airspeed Indicator Markings The airspeed indicator markings are based on Section 5, Airspeed Calibration: Normal Static Source Table. When using the alternate static source, allow for the airspeed calibration variations between the normal and alternate static sources. Marking Value (KIAS) Remarks White Arc 64 - 110 Full Flap Operating Range Lower limit is the most adverse stall speed in the landing configuration. Upper limit is the maximum speed permissible with flaps extended. Do not use flaps above 17,500 feet MSL. Green Arc up to 17,500 feet MSL 25,000 feet MSL 74 - 176 74 - 150 Normal Operating Range Lower limit is the maximum weight stall at most forward C.G. with flaps retracted. Upper limit is the maximum structural cruising speed (V NO ). V NO and upper limit of green arc is reduced linearly from 17,500 feet to 25,000 feet. Yellow Arc up to 17,500 MSL 25,000 feet MSL 176 - 205 150 - 175 Caution Range Operations must be conducted with caution and only in smooth air. Upper and lower lim- its of yellow arc are reduced linearly from 17,500 feet to 25,000 feet. Red Line up to 17,500 feet MSL 25,000 feet MSL 205 175 Never Exceed Speed (V NE ) Maximum speed for all operations. V NE and red line is reduced linearly from 17,500 feet to 25,000 feet. Original Issue 2-6 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Powerplant Limitations Engine Number of Engines.............................................................................. 1 Engine Manufacturer ........................................... Teledyne Continental Engine Model......................................................................TSIO-550-K Engine Type......... Turbocharged, direct drive, fuel injected, air cooled, horizontally opposed 6 cylinder engine with 550 cubic inch displacement. Horsepower Rating.............................................. 315 bhp @ 2500 rpm Oil Temperature ........................................... 240 °F (116 °C) maximum Minimum Oil Temperature for Takeoff...............................75 °F (24 °C) Oil Pressure: Minimum ............................................................................... 10 psi Maximum ............................................................................ 100 psi Operating Limits Do not reduce manifold pressure below 15 inches when above 18,000 ft MSL. Approved Oils: Engine Break-In: For first 25 hours of operation or until oil consumption stabilizes use straight mineral oil conforming to MIL- C-6529. If engine oil must be added to the factory installed oil, add only MIL-C-6529 straight mineral oil. After Engine Break-In: Use only oils conforming to Teledyne Continental Specification SAE J 1899 (Ashless Dispersant Lubrication Oil). All Temperatures ............................... 15W-50, 20W-50 or 20W-60 Above 40 °F (4 °C)...............................SAE 50, 20W50, or 20W60 Below 40 °F (4 °C) ................. SAE 30, 10W30, 15W50, or 20W50 Original Issue Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-7 P/N 13772-005 2-7 Fuel Grade: Aviation Grade 100 LL (Blue) or 100 (green) • Note • Refer to Fuel Limits in this Section for operational limitations regarding fuel and fuel storage. Propeller Hartzell Compact Series Lightweight Hub with Composite Blades Propeller Type ........................................ Constant Speed, Three Blade Model Number..............................................PHC-J3Y1F-1N/N7605(B) Diameter........................................................................................78.0" Model Number........................................... PHC-J3Y1F-1N/N7605C(B) Diameter........................................................................................78.0" Weight Limits Maximum Takeoff Weight ......................................... 3600 lb (1633 Kg) Maximum Weight in Baggage Compartment.................. 130 lb (59 Kg) Maximum Zero Fuel Weight ..................................... 3400 lb (1542 Kg) Original Issue 2-8 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Engine Instrument Markings & Annunciations The following describes the engine instrument markings. Associated Warning and Caution Annunciations are shown in capitalized text. PowerPlant Instrument (Range & Units) Red Arc/Bar Yellow Arc/Bar Green Arc/Bar Yellow Arc/Bar Red Arc/Bar Lower Warning Range Minimum Caution Range Normal Range Maximum Caution Range Upper Warning Range Cylinder Head Temperature (100°F – 500°F) –– –– 240 – 420 420 – 460 CHT > 460 CHT Engine Speed (0 – 3000 RPM) –– –– 500 – 2550 –– > 2550 RPM Exhaust Gas Temperature (1000°F – 1800°F) –– –– 1000–1800 –– –– Manifold Pressure (10 – 40 in.Hg) –– –– 15.0 - 36.5 36.5 - 37.5 37.5 - 40.0 Oil Pressure (0 – 100 PSI) 0 – 10 10 – 30 OIL PRESS 30 – 60 60 – 100 > 100 OIL PRESS Oil Temperature (75°F – 250°F) –– –– 100 – 240 –– > 240 OIL TEMP Percent Power (0 – 100%) –– –– 0 – 100 –– –– Turbocharger Inlet Temperature (1000°F - 1800°F) –– –– 1000 – 1750 –– 1750 -1800 TIT Original Issue Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-9 P/N 13772-005 2-9 Fuel * Dynamically changes based on engine parameters. Electrical Instrument (Range & Units) Red Arc/Bar Yellow Arc/ Bar Green Arc/ Bar Yellow Arc/ Bar Red Arc/Bar Minimum Minimum Caution Range Normal Range Maximum Caution Range Maximum Fuel Flow (0 – 45 U.S. Gal./Hr.) –– –– *See Note –– –– Fuel Totalizer (U.S. Gallon) N < 9 FUEL QTY 9 – 18 > 18 –– –– Fuel Quantity Gage (0 – 46 U.S. Gallon) 0 10 – 14 14 – 46 –– –– Instrument (Range & Units) Red Arc/Bar Yellow Arc/Bar Green Arc/ Bar Yellow Arc/Bar Red Arc/Bar Minimum Minimum Caution Range Normal Range Maximum Caution Range Maximum Essential Bus Volts (0 – 36 Volts) 0 – 24.4 ESS BUS –– 24.5 – 32 –– > 32 ESS BUS Main Bus 1 Voltage (0 – 36 Volts) –– 0 – 24.4 M BUS 1 24.5 – 32 –– > 32 M BUS 1 Main Bus 2 Voltage (0 – 36 Volts) –– 0 – 24.4 M BUS 2 24.5 – 32 –– > 32 M BUS 2 Alternator 1 Current (0 – 100 Amps) –– –– 2 – 100 0 – 1 ALT 1 –– Alternator 2 Current (0 – 100 Amps) –– –– 2 – 100 0 – 1 ALT 2 –– Battery 1 Current (-59 to 59 Amps) –– –– -4 – 59 -59 to -5 BATT 1 –– Original Issue 2-10 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Center of Gravity Limits Reference Datum ................................... 100 inches forward of firewall Forward ...................................................................Refer to Figure 2-1 Aft ............................................................................Refer to Figure 2-1 Figure 2-1 CG Envelope 2000 2200 2400 2600 2800 3000 3200 3400 3600 C.G. - Inches Aft of Datum Weight - Pounds 12.5% MAC FS 139.1 2700 lb 9.8% MAC FS 137.8 2100 lb 31.5% MAC FS 148.2 2100 lb 21.1% MAC FS 143.2 3600 lb 31.5% MAC FS 148.2 3600 lb Max Zero Fuel 138 136 140 142 144 146 148 150 SR22_FM02_3216 FORWARD LIMIT - The forward limit is FS 137.8 (9.8% MAC) at 2100 lb, with straight line taper to FS 139.1 (12.5% MAC) at 2700 lb, to FS 143.2 (21.1% MAC) at 3600 lb. AFT LIMIT - The aft limit is FS 148.2 (31.5% MAC) at all weights from 2100 lb to 3600 lb. Original Issue Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-11 P/N 13772-005 2-11 Maneuver Limits Aerobatic maneuvers are prohibited. Spins are prohibited. This airplane is certified in the normal category and is not designed for aerobatic operations. Only those operations incidental to normal flight are approved. These operations include normal stalls, chandelles, lazy eights, and turns in which the angle of bank is limited to 60°. • Note • Because the aircraft has not been certified for spin recovery, the Cirrus Airframe Parachute System (CAPS) must be deployed if the airplane departs controlled flight. Refer to Section 3, Inadvertent Spin Entry. Flight Load Factor Limits Flaps UP (0%), 3600 lb. .....................................................+3.8g, -1.9g Flaps 50%, 3600 lb................................................................. +1.9g, 0g Flaps 100%, 3600 lb............................................................... +1.9g, 0g Minimum Flight Crew The minimum flight crew is one pilot. Revision 1 2-12 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Kinds of Operation The aircraft is equipped and approved for the following type operations: • VFR day and night. • IFR day and night. Kinds of Operation Equipment List The following listing summarizes the equipment required under Federal Aviation Regulations (FAR) Part 23 for airworthiness under the listed kind of operation. Those minimum items of equipment necessary under the operating rules are defined in FAR Part 91 and FAR Part 135 as applicable. • Note • All references to types of flight operations on the operating limitations placards are based upon equipment installed at the time of Airworthiness Certificate issuance. System, Instrument, and/ or Equipment Kinds of Operation Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Placards and Markings Airplane Flight Manual (Included w/ POH) 1 1 1 1 Communications VHF COM — — 1 1 Electrical Power Battery 1 1 1 1 1 Battery 2 — — 1 1 Alternator 1 1 1 1 1 Alternator 2 — — 1 1 Amp Meter/Indication 1 1 1 1 Original Issue Cirrus Design Section 2 SR22T Limitations P/N 13772-005 2-13 P/N 13772-005 2-13 Low Volts Annunciator 1 1 1 1 ALT 1 Annunciator 1 1 1 1 ALT 2 Annunciator — — 1 1 Circuit Breakers A/R A/R A/R A/R As required. Equipment & Furnishings Emergency Locator Trans- mitter 1 1 1 1 Restraint System A/R A/R A/R A/R One seat belt for each occupant. Fire Protection Fire Extinguisher 1 1 1 1 Flight Controls Flap Position Indicator 1 1 1 1 Flap System 1 1 1 1 Pitch Trim Indicator 1 1 1 1 Pitch Trim System 1 1 1 1 Roll Trim Indicator 1 1 1 1 Roll Trim System 1 1 1 1 Stall Warning System 1 1 1 1 Fuel Auxiliary Fuel Pump 1 1 1 1 Fuel Quantity Indicators 2 2 2 2 Fuel Selector Valve 1 1 1 1 System, Instrument, and/ or Equipment Kinds of Operation (Continued) Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Original Issue 2-14 P/N 13772-005 Section 2 Cirrus Design Limitations SR22T Ice & Rain Protection Alternate Engine Air Induc- tion System 1 1 1 1 Alternate Static Air Source 1 1 1 1 Pitot Heater — — 1 1 Landing Gear Wheel Pants — — — — May be removed. Lights PFD Bezel Lighting — — — 1 PFD Backlighting * 1 1 1 *Required if MFD Backlighting Fails. Engine Indicators Must Be Shown in Backup Mode. MFD Bezel Lighting — — — 1 MFD Backlighting * 1 1 1 *Required if PFD Backlighting Fails. Engine Indicators Must Be Shown in Backup Mode. Anticollision Lights 2 2 2 2 Instrument Lights — 1 — 1 Navigation Lights — 2 — 2 Landing Light — 1 — 1 For hire opera- tions. Flash Light — 1 — 1 System, Instrument, and/ or Equipment Kinds of Operation (Continued) Remarks, Notes, and/or Exceptions VFR Day VFR Nt. IFR Day IFR Nt. Original Issue